Flow controlling valve system



June 7, 1960 J. R. CONYERS 2,939,281

FLOW CONTROLLING VALVE SYSTEM Filed March l, 1954 JOHN R. CONYERS BY WMM/fw ATTORNEY 2,939,281 FLOW 'CONTROLLING VALVE SYSTEM John R. Conyers, Reseda, Calif., assignor to North AmericanAvation, Inc.

Filed Mar. 1,1954, Ser. No. 413,045 12 Claims. (Cl. Gil-397.48)

This invention relates to a valve system for controlling the ow of a liquid or gas. The invention more particularly relates to the provision of a valve system for controlling the How of propellants into the combustion chamber of a rocket engine. Designs of small rocket engines have incorporated therein a gas orair-pressurized propellant feed system for delivery of an oxidizer and the fuel to the injector of the rocket engine thrust chamber. In a pressurized feed system, a pressurizing means, which is normally a gas generator of the igniter or self-contained type, pressurizes farice Y the soft start is the attainment of ignition and the rise to operational chamber pressure without an excessive pressure surge or detonation taking place in theA combus tion' chamber. The dominating requirement for a soft start is to initiate the flow of propellant through theV injector at a minimum rate and pressure which Will'start a reliable ignition, and then to smoothly increase the flow rateA and pressure of the propellants until full thrust chamber combustion is realized.

A principal object of this invention is to obtain a new and novel flow-controlling valve system.

vA further object of this invention is to provide a valve system for conducting a liquid or gas to an injector. p

Astill further object of this invention is to provide a low pressure burst valve system which will withstand high pressureV when the burst valve is supported by a sliding n member.

changes in volume of the tank liquids due to an increase 3 inambient temperature. Thus, the propellent tanks are at times under a relativelyh'igh pressure in the prering condition. This pre-tiring condition in a propellent tank necessitates undesirably high rupture strength in the burst diaphragms of the propellent feed lines. When the tiring sequence is initiated in these systems the pressurizing medium has to build up the propellent pressure to an undesirable high value in order to open the burst diaphragms. Asurge of propellants is then injected into the combustion chamber and an excessive amount accumulates. before combustion is suciently advanced to handle it. 4

Another undesirable result of using these previous high-pressure burst diaphragms is the non-uniform open` ing of'one propellent line in relation to the other. This results in an oit mixture ratio at the start of the engine and an unintended oxidizer or fuel leadin the combustion process.

The many diiliculties inherent in prior rocket valve systems are overcome by the instant invention. A pressure-actuated valve is provided which will support a low-strength burst diaphragm against rupture Vuntil the opening operation is scheduled in the starting sequence. During all pre-tiring conditions, the vlow-strength burst diaphragm is protected from rupture by having a support positioned behind it. A flow of the pressurizing medium is utilized to remove the support behind the burst diaphragm in order that the diaphragm will be able to rupture and open at a comparatively low propellant pressure. Thus, the propellant does not surge as it enters the combustion chamber, but the -flow and pressure is permitted to start at a low value and to increase progressively. *The present invention in its specific aspects allows ,a rocket engine to make a so-called soft start. Basically;L

2A further object of this invention is to provide for a soft start in a rocket power plant.

An object of this 4invention is vto provide a means for employing a low-strength burst diaphragm in a propellent feed line. A further object of this invention is to provide improved control `of the propellent flow into a rocket power plant bythe utilization of the action of gas pressure on a large diameter, piston-type injector.

A still further object of this inventionis to provide a sliding injector assembly as asliding support in back of low pressure burst diaphragms.

Another object of this invention is to provide a smooth starting rocket engine. v Y y A further object of this invention is to provide a smooth starting rocketV engine which will incorporate a transitional combustion stage.

A still further object of this invention is to provide means to protect low rupture pressure diaphragms from bursting at high pressures under non-operating conditions.

Other objects of invention will become apparent from the following description taken in connection with the accompanying drawings, in which Fig. l represents the general valve system for controlling a liquid or gas ow;

Fig. 2 shows an intermediate locking device for stepwise valve control of va liquid or gas How;

Fig. 3 represents the use of a speciiic valve system in a rocket, and

Fig. 4 represents a detailed view of the valve system of Fig. 3. v

The flow controlling valve system illustrated in Fig. l comprises a rigid cylindrical casing member 10 having peripheral openings 15 therein and 'a piston slidable within said cylindrical casing member. The piston member serves as an injector to inject a fluid or gas intora desired chamber. The injector comprises a support p0rtion 12 and an entrance portion 13. The support portion 12 is of solid material, while the entrance portion 13 comprises a series of liquid conducting ports or grooves leading to injector nozzles 13a. Suitable means 19a are provided for slidingly sealing the injector with respect to the cylindrical member. Situated between and in abutting relationship with the interior periphery of the apertures 15 and the solid portion 12 of the injector is a thin shell member 16 which functions as a normally closed valve or burst diaphragm. In 'preoperating position the thin shell member or burst diaphragm 16 is supported by the support portion 12 in proximity to and juxtaposition with the peripheral aper` tures 15. The thin shell member or burst diaphragm 16 has a relatively low rupture strength. By reason of the support 12 being placed in abutting relationship behind the 16, Vthediaphragm is able to*withstaiini"V pressuresv greater than its calibratedfbu'rst strength.

Fig. 1 further shows conduit means 14 through which a pressuriains meansacts against the burst diaphragm 1.6...

Lafthelcase .of rlcket installations; Pressure/,on the; lproipeil'irtts.tlgiemselvesV cause thepropellants to ogw through channelsjlli and `create a pressure throughthe 'openings l15` Yandagainst the burst diaphragm 16. i In', normal operation'the low pressure'burst diaphragm can withstandfrelatively high pressures because yof the presence of the supporting member behind the 'burst diaphragm.

When'it is desired that the normally closed valve be opened, pressurized gas is introduced into the space v11 through conduit and valve means a above the injector piston. vThis pressurizedV gas .forces the .piston to move with `respect to the cylindricalV member, removing the vsupportv portion of the. piston from rin backV of the dia- Vphragm where, theY diaphragm isin juxtaposition withthe opening 15.1A positive Ystop,means19 isV provided to limit travel of'said injector. Likewise, a mechanical detent and groove combination17, 18 is provided to lock 'assaggi 1 aspects as/related to use in rocket construction. The valve system illustrated in Fig. V4 comprises a slidinginjector 41, having supportportions 61 and 62 and entrance portions 46 and y47. The injector 41 slides within a rigid cylindrical member 42 and is slidingly sealed therewith by means 60. A thin shell member or burst diaphragm `44 is provided between `the injector 41 and the cylindrical member 42. 'The 'burst diaphragm 44 as illustratedzprovides normally-closed valves acrosstherperipheralv openings/ 45 and the cylindrical member 42. In normal pre-firing operatin..thesupport portions 61 and 62 of the injectoriabuts against` the burst diaphragm 44 at a point in juxtaposition withibothfthe Vburst diaphragm 44 and the openings y45. In prefiring operation, pressures developed in` variouspropellent'tank sections, separated by walls 54 and 55, and transmitting pressures to the openings 45 by channels formed by barriers 52 and 453, are prevented from bursting the thin `shellmember the piston with respect to the cylindrical member at itsy and means to Ypressurize the liquid or gas which flowsV through the conduit 14, the openings v and burst diaphragm .16, when ,theVV injector is in lthe bottom position,

' maybe a common'pressurizing means. n A suitable pressurizing means maybe seen in Fig. 31asexplained below. lFig. 2 illustrates an` intermediate locking ydevice for step-wise valve control of the fluid ow into the injectorY and Athrust chamber. ,In this modification, a shear pin or other restraining device 7,5 is placed in the path of the injector '12,13 sliding withV respect to theV cylindrical 'member 10. Y This will allow only a partialV juxtaposition ofthe-entrance portions `13, and the peripheral 'openings 15'ar1d result in a partial combustion rate in the thrust chamber. As the pressure inthe feed system and in the space 11 (Fig. l) increases Vto a predetermined amount the shear pin or restraining means 75 fails and the inject'o'r'continues its movement until it abuts limit stop 1 9 while simultaneously putting the entranceportionsla and openings 15 in juxtaposition and lockingV the ,piston injector with respect to the cylindrical member 10. InV

Fig. 2 the locking is accomplished by a split ring 1 expanding, into the groovev18. Y

fig. 3 showsrarspecic use of the ow controlling valve invention. The rocket illustrated in Fig.; 3V includes a warhead 21, an igniter or other type gasY generator 22, a pressure exhausttube v2,3, adeector portion 24, propellent tanksY and 26 separated by a flexible wall 27,v

an injector assembly 29, locking and abutting means 30,

31v for VtheA sliding injector 29, Va combustion or thrustv chamber-32', a throat section 33, and anV exhaust andV tail j common pressurizing means to pressurize both tank sections. Simultaneously, with the emission of pressurizing gasV downthe ktube 23, pressurizing gas Valso vlltravels through aperture 28 and forces the'sliding injector innan aftV direction, This action removes the supports from the injector burst diaphragrns, explained with respect to Fig."` 4 below, and' allows injection of the pressurized propellants into the thrust chamber 32..

l: Fig. 4"-is a detailed viewof the invention in its specific u 44Yby reason of the supports 61 and 62abutting' the rear of, such shell member atthe area of the peripheral apertures 45: y

'A-t the start of the firing sequence, the piston-like injector 41 is slid in an aft direction compressing a compressible ring 5S and bringing the entrance portions or grooves 46 and 47 into juxtaposition with the peripheral openings 45. As the ring 58 is compressed to afull extent, a mechanical detentjmeans, such as a spring split ring v57, falls into a groove `59, to eectively lock the injector v41 with respect to the cylindrical member`42.

Simultaneously, with this' action, the removal of the Vsupport, lportions 6'1 and 62 from behind the burst diaphragrnsY in, proximityY to the openings 45V allows such burst diaphragrns to burst, and allows flow of thev liquid Ypropellants through the entrance portions 46 and 47, and

into the injector nozzles 48 and 49. Fuel and oxidizer are typically injected into the'area 50 of the combustion chamber 51 and the resultant gases are expelledl through I, 'the throat sections aftof the chamber 51 and provide theF necessary thrust for the rocket. This Vactioncan be seen in Fig. 3. Y A 'I Y vThe valve systems described in Fig. Yl and Fig. 4 incorporate a two-positionsliding injector. It is further Y contemplated by this invention that a transitional or inillustratedin Fig. '2.' Thus, the shearing action or burst- The'v above set out invention Vis not limited to valve i systems for controlling propellent llow Vto rockets. The

valve system may beV used to control the ow of a liquid or a gas Vto a Vliquid Vreactantv Ygas generator system or power unit, or to any other demand for a normally-closed .Y valve system, with ability to hold high pressures, Vyet able to beopened by pneumatically or hydraulically actuated devices to deliver a flow. of liquid or gas which builds up from the initial, pressure in the valve system.

Although the' invention has been described and illustrated in detail, it is to be clearly understood that the same is Vby way ofV illustration andexample only and is not to be taken by way of limitation, the spirit andrscope of this invention being limited only by the terms ofthe appended claims. l

I claim:

1. A how-controlling valve system comprising 'a rigid casing member having at Ieast'one opening therein, means to conduct a ow of fluid through the' opening, a burst able diaphragm closing the opening, a slidable injector within said casing memberand having a solid support portionr and an entrance portion, saidY solid portionrbeing positioned tonormally abutcagainst said diaphragm and associated opening, said injector being slidable into a position whereby the support portion is removed from abutment with said diaphragm and the entrance portion is in juxtaposition with said opening, `and pressurizing means for bursting said diaphragm and to allow ow of iluid from said rst-mentioned means to said injector.

2. A dow-controlling valve system comprising a cylindrical casing member having at least one opening therein, a sliding injector member within said casing member and having a support portion and an entrance portion, a diaphragm member disposed between the casing opening and the support portion of said injector member, means to move said injector so that the entrance portion is in juxtaposition with said opening and the support portion is removed 'om juxtaposition with said opening and diaphragm, and means to burst said diaphragm when said injector support portion is removed therefrom.

3. The invention as claimed in claim 2 in which the last two mentioned means are a common pressure means.

4. The invention as claimed in claim 2 in which a locking means is provided for locking said injector with respect to said casing member after the support portion has been removed from juxtaposition with said opening and diaphragm.

`5. In a rocket engine having a pressurized propellant feed system and thrust chamber, at least one propellant tank, a rigid cylindrical member having at least one opening in the periphery thereof leading to said tank, a sliding injector having a support portion and an entrance portion, a thin `shell member situated between and abutting the support portion of the injector and the peripheral opening in the cylindrical member, and means to slide said injector with respect to the cylindrical member and to thereby remove the support portion thereof from juxtaposition with said opening and from supporting the thin shell member at said opening, said mean sliding said injector to a position wherein said entrance portion is opposite said peripheral opening.

6. The invention as claimed in claim 5 in which a means to pressurize the propellant tank is provided, which means further functions to slide the injector.

7. The invention as claimed in claim 6 in which a means is provided to lock the injector with respect to the cylindrical member when the entrance portion of the injector is opposite the peripheral opening.

V8. The invention as claimed in claim 6 in which the pressurizing means bursts the thin shell member when the support portion of the injector is removed from juxtaposition with the peripheral opening and the shell member.v

9. lIn a pressurized fluid feed system, a rigid cylindrical casing member having a plurality of openings around the periphery thereof, a piston-like injector, having support portions and grooved entrance portions, within the casing member, a thin cylindrical shell member disposed between and abutting the openings and the support portions of the injector, means to remove said support portions from abutting relation with said shell holder at said openings, said last-mentioned means moving said entrance portions into juxtaposition with said openings, and locking means to lock said injector with respect to the casing member when said entrance portions are in juxtaposition with said openings, said thin cylindrical shell member being adapted to burst at low pressures when the support portions of said injector are removed from juxatposition with said peripheral openings.

10. The invention as claimed in claim 9 in which an intermediate restraining means is provided to allow partial juxtaposition of both said support portions and said entrance portions with said peripheral openings.

11. A flow-controlling valve system comprising a cylindrical member having at least one opening in the periphery thereof, a piston member slidable Within said cylindrical member, a normally sealed valve abutting and between said opening and a peripheral surface of said piston, said piston being slidable to remove at least part of the peripheral surface thereof from abutting relation with the valve at the area of the peripheral opening, and pressure means to open said valve when said piston has been moved.

l2. The invention as claimed in claim l1 in which the pressure means moves said piston, opens said valve, and controls the flow of a liquid through said opening, said valve and into said piston.

References Cited in the le of this patent UNITED STATES PATENTS 1,863,455 Rowley June 14, 1932. 2,502,886 Ragan i Apr. 4, 1950 2,671,312 Roy v Mar. 9, 1954 

